Miniature spacecraft

ABSTRACT

A miniature spacecraft is constructed using modular features so as to provide a wide range of possible sizes with a choice of physical attributes. Radially directed bays are arranged around a central cylindrical element which may be used for storing a propulsion tank or canister. Octagonal or other configurations provide rigidity and strength through the use of triangular planetary cylinders which form outwardly facing bays for storage.

The present application is a continuation of application Ser. No.09/371,784 now U.S. Pat. No. 6,131,857, filed Aug. 10, 1999.

This application claims the filing date of a previously filedprovisional patent application having Ser. No. 60/106,340 and anassigned filing date of Oct. 30, 1998 as well as Disclosure Documentshaving Ser. Nos. 442,563, 448.685, 448,677 and 448,678 having filingdates of Jul. 23, 1998, Dec. 15, 1998, Dec. 15, 1998 and Dec. 15, 1998respectively, which applications and disclosures containing subjectmatter substantially the same as that described and claimed in thepresent application.

BACKGROUND OF THE INVENTION

1. Field of the Invention

This invention relates generally to aircraft and particularly to craftdesigned for operation in a low gravity environment such as space craft,and more particularly to a miniature space craft of specific modularconstruction adapted for structural expansion for a variety ofapplications.

2. Description of Related Art

The following art defines the present state of this field:

Devlin, U.S. Pat. No. 3,709,447 describes a satellite apparatus wherebya plurality of experiments may be monitored in a single satellite for aplurality of different organizations. The satellite has modular casingsfor placement on a frame and adapted to place experimental componentstherein with instrumentation facing a centrally located scanner whichtransmits data on the experiments to a receiving station.

Perkins et al., U.S. Pat. No. 5,271,582 describes multiple subsidiarysmall payloads connected to standard mechanical and electricalinterfaces provided by an expendable or recoverable modular mothersatellite bus (MMSB) and launched into space as an assembly acting as acommon carrier providing low unit launch costs for the attachedsubsidiary payloads and also providing a variety of electrical,pointing, and thermal control services for these payloads after reachingorbit. These services include but are not necessarily limited tocontrolled separation of free-flying satellites or re-entry vehicles,regulated electric power at a variety of voltages, telemetry, computercontrol, payload control via time delayed pre-programmed instructions,optional real-time payload control via direct radio communication ortransmission through geostationary or other communication satellitelinks, time-driven or event-driven control logic, mass data memory,encryption and decryption of data and commands, payload pointingaugmented heat rejection, and interconnection between subsidiaryattached payloads through the data bus.

Anderson, U.S. Pat. No. 3,596,853 describes a space capsule includingheat source devices individually recoverable in which each heat sourcedevice includes a combined pyramidal-type reentry body and heatreflector and a radioisotopic heat source disposed in a hollow orconcave portion of the body.

Cappa et al., U.S. Pat. No. 5,848,767 describes a single piece frame fora spacecraft, the frame manufactured as fiber composite sheets overlay acore. The core is preferably made of aluminum and formed with ahoneycomb cross-section. The frame provides a mounting structure towhich payload, spacecraft equipment, and boost vehicle are attached. Theframe can be reinforced locally by varying the core density or the wallthickness so as to resist concentrated or localized loads. Theorientation of the fiber in the composite sheets may also be varied soas to so as to strengthen the frame in a desired location.

Esch et al., U.S. Pat. No. 3,258,225 describes a satellite structurecomprising, a frame comprising a plurality of frame sections, sidepanels carried by the frame and supported in said frame sections, a toppanel closing the upper end of the frame, a bottom panel closing thelower end of the frame and having a central opening, a metallic baseplate closing the opening, and satellite instrumentation supportingmeans mounted on the base plate and having its upper end secured to thetop panel.

Chatelain, U.S. Pat. No. 3,153,235 describes a reflector antenna havinga hollow, expansible polyhedral body consisting of a plurality ofinwardly extending recesses.

Kamm, U.S. Pat. No. 3,168,263 describes a satellite vehicle orientationdevice comprising a satellite vehicle, a rigid, elongated tubular memberhaving one end fastened to said satellite vehicle, a reel for storingsaid tubular member and means for deploying said tubular member.

The prior art teaches various spacecraft construction schemes. However,the prior art does not teach that a miniature spacecraft may beconstructed with a central cylindrical bay having radially orientedtriangular bays for forming open bay areas facing outwardly. The presentinvention fulfills these needs and provides further related advantagesas described in the following summary.

SUMMARY OF THE INVENTION

The present invention teaches certain benefits in construction and usewhich give rise to the objectives described below.

The present invention provides a miniature spacecraft constructed usingmodular features so as to provide a wide range of possible sizes with achoice of physical attributes. Radially directed bays are arrangedaround a central cylindrical element which may be used for storing apropulsion tank or canister. Octagonal or other configurations providerigidity and strength through the use of triangular planetary cylindersforming outwardly facing bays for storage.

A primary objective of the present invention is to provide a miniaturespacecraft having advantages not taught by the prior art.

Another objective is to provide such a craft having octagonal symmetryfor strength and adaptability.

A further objective is to provide such a craft having radialconstructional features for strength.

A still further objective is to provide such a craft having triangularwall structures for rigidity.

A yet further objective is to provide such a craft having a centralcylindrical bay capable of storing a payload such as a propulsioncanister.

Other features and advantages of the present invention will becomeapparent from the following more detailed description, taken inconjunction with the accompanying drawings, which illustrate, by way ofexample, the principles of the invention.

BRIEF DESCRIPTION OF THE DRAWING

The accompanying drawings illustrate the present invention. In suchdrawings:

FIG. 1 is an exploded perspective view of the preferred embodiment ofthe present invention; and

FIG. 2 is a perspective view thereof showing the invention as assembled.

DETAILED DESCRIPTION OF THE INVENTION

The above described drawing figures illustrate the invention, aminiature spacecraft apparatus 10 comprising a rigid structural andsymmetrical body portion 20 including plural walls 30 arranged to forman open central cylindrical wall enclosure 40. The preferable materialsused in the present invention are high strength composite sheet stock.Appended to, and extending radially outwardly from the centralcylindrical wall enclosure 40 are a plurality of spaced apart planetarycylindrical wall enclosures 50 best seen in FIG. 1. The planetarycylindrical wall enclosures 50 are arranged for defining generallyrectangular volumes 55 therebetween, the rectangular volumes 55 beingpositioned for access from at least four opposing sides of the apparatus10 as shown in FIGS. 1 and 2. A top 60 and a bottom 70 plates areengaged with the body portion 20 and the planetary wall enclosures 50 inpositions for enclosing the central cylindrical wall enclosure 40 andthe planetary cylindrical wall enclosures 50. The plates 60, 70 providepartial enclosure also to the rectangular volumes 55 such that thesevolumes are accessible only from the apparatus' periphery as can best beseen in FIG. 2. Bonding agents are used to fasten the various elementsof the invention to one another in a permanently attached fashion. Acylindrical storage pod 80 is positioned within the central cylindricalwall enclosure 40, the storage pod 80 providing a means for lateralstructural reinforcement 82; the three flanges shown in FIG. 1, suchthat forces applied to the storage pod 80 are transferred through thelateral reinforcement means 82 to the cylindrical wall enclosure 40. Aclosed cylindrical storage vessel 90 is enclosed within the storage pod80 by the top and bottom plates 60, 70 the storage vessel 90 providing afluid valving means 95 extending outwardly from a pass-through means 100in at least one of the plates 60, 70 as shown. The fluid valving means95 shown is only one possible propulsion device useful in conjunctionwith the present space craft and is intended to show how such a meansmay be enabled. The capping device 110 illustrates a means forstructurally supporting the valving means 95.

The planetary cylindrical wall enclosures 50 each inventively comprise atriangular arrangement of structural wall sections 52 providing a highlyrigid structure. The storage pod 80 comprises a circular wall element 81integral with the plurality of lateral reinforcement means 82 whichextend radially outwardly therefrom. The top and bottom plates 60, 70and the planetary cylindrical wall enclosures 50 are of suchconformation as to establish the apparatus preferably with eight sidesof equal length and arranged symmetrically about a longitudinal axis 56of the apparatus 10. The top and bottom plates 60, 70 and the planetarycylindrical wall enclosures 50 may alternately be of such conformationas to establish the apparatus 10 with a circular exterior shape or apolygon configuration other than an octagon. Clearly, the apparatus maybe constructed in alternate perspective, i.e., with a smaller or largerrelative height dimension. Also, the instant basic construction lendsitself to a modular adaptation, so that, for instance, two of bodyportion 20 may be used to erect a space craft of twice the height shownin FIG. 2. Such a craft would utilize two of storage pod 80 as well anda storage vessel 90 with approximately twice the length as the vesselshown in FIG. 1.

Because of its basic and modular construction, the spacecraft of thepresent invention may be used for a very wide range of applications. Thevolumes 55 (storage bays) may be used for equipment or general storageand the other interior spaces may be utilized for necessary equipmentand systems for enabling useful spacecraft functions. In suchutilization a method is herein defined for equipping the spacecraft withoperational components, said method including: providing the instantspacecraft with its centrally located equipment bay surrounded by theplurality of radially oriented equipment bays, through placement,interconnection or other accommodation, both mechanical and electrical,and by any of the well known prior art interconnection means andtechniques: a modular electrical power package, a modular propulsionpackage, a modular communications package, a modular sensory andmonitoring package, a modular deployable vehicle package and a modularattitude control package, each of the foregoing in at least one of theequipment bays. It should be noted that these items are listed here forreference purposes only and do not constitute an exhaustive orcomprehensive list of such items. The items are also, of any of the wellknown types so that further details of construction, function orinterconnectivity are not herein provided. The method further providesfor fastening the top and bottom plates to the body portion by aplurality of removable fasteners so as to enable-replacement of theplates with alternative spacecraft equipments such as space sails, solarpanels, antennas and other related exterior spacecraft systems.

While the invention has been described with reference to at least onepreferred embodiment, it is to be clearly understood by those skilled inthe art that the invention is not limited thereto. Rather, the scope ofthe invention is to be interpreted only in conjunction with the appendedclaims.

What is claimed is:
 1. A miniature spacecraft comprising: a symmetricalbody portion including plural walls arranged to form an open centralcylindrical wall enclosure, and appended to the central cylindrical wallenclosure, and extending radially outwardly therefrom a plurality ofspaced apart planetary wall enclosures each said enclosure having agenerally triangular configuration; the planetary wall enclosuresarranged for defining volumes there between; means for enclosing theopen cylindrical wall enclosure and the volumes; the central cylindricalwall enclosure, the volumes and the means for enclosing adapted topermit interconnection and access to the volumes.
 2. The apparatus ofclaim 1 wherein the means for enclosing includes a top plate and abottom plate engaged with the body portion and the planetary wallenclosure, the top plate and bottom plate enclosing the centralcylindrical wall enclosure and providing partial enclosure to thevolumes.
 3. The apparatus of claim 1 wherein the central cylindricalwall enclosure, the volumes and the means for enclosing are adapted forelectrical interconnection of operational components.
 4. The apparatusof claim 1 wherein the central cylindrical wall enclosure, the volumesand the means for enclosing are adapted for mechanical interconnectionof operational components.
 5. The apparatus of claim 1 wherein saidmeans for enclosing is adapted to form a multi-level structure.
 6. Theapparatus of claim 1 wherein said body portion, said wall enclosures andsaid means for enclosing are adapted for modular construction.
 7. Theapparatus of claim 1 wherein the enclosures and volumes are adapted toaccommodate modular equipment packages.
 8. The miniature spacecraft ofclaim 1 wherein said means for enclosing the open cylindrical wallenclosures in the volumes includes exterior spacecraft equipmentfastened to said body portion.
 9. A miniature spacecraft comprising: asymmetrical body portion including plural walls extending radiallyoutwardly from the center to form a plurality of spaced apart walls,arranged to form an open wall enclosure; the spaced apart walls arrangedfor defining volumes there between and adapted for enclosing thevolumes; and the walls adapted for interconnection for providing accessto the volumes.
 10. The apparatus of claim 9 further including a topplate and a bottom plate engaged with the body portion, the top plateand bottom plate enclosing the wall sections, and providing partialenclosure to the volumes; and the top plate and/or bottom plate adaptedfor interconnection with mechanical members and for allowing access tothe volumes.
 11. The apparatus of claim 9 wherein the walls, top plateand/or bottom plate are adapted for electrical interconnection ofoperational components.
 12. The apparatus of claim 9 wherein the walls,top plate and/or bottom plate are adapted for mechanical interconnectionof operational components.
 13. The apparatus of claim 9 wherein thewalls, top plate and/or bottom plate are adapted to form a multi-levelstructure.
 14. The apparatus of claim 9 wherein the walls, top plateand/or bottom plate are adapted for modular construction.
 15. Theapparatus of claim 9 wherein the enclosures and volumes are adapted toaccommodate modular equipment packages.
 16. A miniature spacecraftcomprising: a symmetrical body portion including plural walls arrangedto form an open planetary wall enclosure defining a volume; a top plateand a bottom plate engaged with the planetary wall enclosure and adaptedto enclose the volume there between; the plural walls, the top plate andthe bottom plate adapted for attachment of modular equipment packagesfor allowing mechanical members to be appended thereto, and for allowingaccess to the volumes.
 17. The apparatus of claim 16 wherein the pluralwalls, the top plate and the bottom plate are adapted for electricalinterconnection of operational components.
 18. The apparatus of claim 16wherein the plural walls, the top plate and the bottom plate are adaptedfor mechanical interconnection of operational components.
 19. Theapparatus of claim 16 wherein the top plate and bottom plate are adaptedto form a multi-level structure.
 20. The apparatus of claim 16 whereinthe plural walls are adapted for modular construction.
 21. The apparatusof claim 16 wherein the enclosures and volumes are adapted toaccommodate modular equipment packages.
 22. A miniature spacecraftapparatus comprising: a rigid structural and symmetrical body portionincluding plural walls arranged to form an open central cylindrical wallenclosure, and appended to the central cylindrical wall enclosure, andextending radially outwardly therefrom a plurality of spaced apartplanetary cylindrical wall enclosures each having a generally triangulararrangement of structural wall sections; the planetary cylindrical wallenclosures arranged for defining generally rectangular volumes therebetween, the rectangular volumes being positioned for access from atleast four opposing sides of the apparatus; a top and bottom platesengaged with the body portion and the planetary wall enclosures inpositions for enclosing the central cylindrical wall enclosure and theplanetary cylindrical wall enclosures, the plates providing partialenclosure also to the rectangular volumes; a cylindrical storage podpositioned within the central cylindrical wall enclosure, the storagepod providing a means for lateral structural reinforcement such thatforces applied to the storage pod are transferred through the lateralreinforcement means to the cylindrical wall enclosure.